摘要 :
An axisymmetric air intake system for a jet aircraft engine comprising a fixed cowl extending outwardly from the face of the engine, a centerbody coaxially disposed within the cowl, and an actuator for axially displacing the cente...
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An axisymmetric air intake system for a jet aircraft engine comprising a fixed cowl extending outwardly from the face of the engine, a centerbody coaxially disposed within the cowl, and an actuator for axially displacing the centerbody within the cowl was developed. The cowl and centerbody define a main airflow passageway therebetween, the configuration of which is changed by displacement of the centerbody. The centerbody includes a forwardly-located closeable air inlet which communicates with a centerbody auxiliary airflow passageway to provide auxiliary airflow to the engine. In one embodiment, a system for opening and closing the centerbody air inlet is provided by a dual-member centerbody, the forward member of which may be displaced axially with respect to the aft member.
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摘要 :
A computer program is presented and described that generates jet engine inlet flow contour maps and inlet flow distortion parameters. The program input consists of an array of measurements describing the flow conditions at the eng...
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A computer program is presented and described that generates jet engine inlet flow contour maps and inlet flow distortion parameters. The program input consists of an array of measurements describing the flow conditions at the engine inlet. User-defined distortion parameters may be calculated.
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摘要 :
Transient airflow is a primary parameter required to evaluate propulsion system component matching, stability and control, and transient engine performance. Development and verification of techniques to calculate turbine engine tr...
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Transient airflow is a primary parameter required to evaluate propulsion system component matching, stability and control, and transient engine performance. Development and verification of techniques to calculate turbine engine transient airflow performance have been a difficult, long-term problem. In this study a turbine engine transient airflow simulator was developed and used to evaluate candidate transient airflow measurement systems. Design criteria and analysis procedures are presented for an engine inlet bellmouth and engine subsonic venturi transient airflow measurement system. The recommended systems have nominal transient airflow measurement uncertainties of 1 percent. (Author)
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This report summarizes the work performed during the second year of an AFOSR sponsored research program that was primarily concerned with the development of an analytical technique for determining the radiated sound field from axi...
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This report summarizes the work performed during the second year of an AFOSR sponsored research program that was primarily concerned with the development of an analytical technique for determining the radiated sound field from axisymmetric jet engine inlet configurations. The analytical technique employed is based upon an integral representation of the external (radiation) solutions of the Helmholtz equation which describe the sound fields external to a given body under either no flow or constant velocity flow situations. The integral representation developed during the course of this research program is different from earlier works in the sense that it not only yields the correct (unique) solution for all radiation problems at all frequencies, but that the resulting integral equations contain no strong (i.e., nonintegrable) singularities and therefore can be solved by straight forward numerical techniques.
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The material in this book has been assembled to support a Lecture Series presented by the authors at the Wright-Patterson Air Force Base,Ohio (USA),Toulouse (France),Munich (Germany) and London (UK). The papers presented review th...
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The material in this book has been assembled to support a Lecture Series presented by the authors at the Wright-Patterson Air Force Base,Ohio (USA),Toulouse (France),Munich (Germany) and London (UK). The papers presented review the basic concepts related to the optimization of airplane installations. The following problems are considered: inlet-airframe interference,nozzle-airframe interference,engine integration and thrust drag definition. (Author)
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This research investigates the effects of inlet dump angle on the size, shape, location and magnitude of recirculation zones for single side dump Pulse Detonation Combustor detonation tubes and describes the methods and results of...
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This research investigates the effects of inlet dump angle on the size, shape, location and magnitude of recirculation zones for single side dump Pulse Detonation Combustor detonation tubes and describes the methods and results of hypothesized improvements to the internal flow path of those engines to ensure complete inter-cycle quenching. Additional analysis was conducted to visualize the dispersion of fuel along the feed tube and into the dump region as a means of providing initial validation of the design with respect to appropriate fuel concentration within the geometry.
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Contents: Introduction Air-breathing jet engines without compressor Air-breathing jet engines with compressor Application of the air-breathing jet engine in rocket technology A brief historical survey of air-breathing jet engines ...
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Contents: Introduction Air-breathing jet engines without compressor Air-breathing jet engines with compressor Application of the air-breathing jet engine in rocket technology A brief historical survey of air-breathing jet engines and prospects of their development Literature.
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